EP3505725B1 - Rohrbrenner für eine gasturbine und gasturbine mit solch einem rohrbrenner - Google Patents

Rohrbrenner für eine gasturbine und gasturbine mit solch einem rohrbrenner Download PDF

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Publication number
EP3505725B1
EP3505725B1 EP18215866.7A EP18215866A EP3505725B1 EP 3505725 B1 EP3505725 B1 EP 3505725B1 EP 18215866 A EP18215866 A EP 18215866A EP 3505725 B1 EP3505725 B1 EP 3505725B1
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EP
European Patent Office
Prior art keywords
combustor
tubular body
inner tubular
combustion chamber
burner
Prior art date
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EP18215866.7A
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English (en)
French (fr)
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EP3505725A1 (de
Inventor
Michael Thomas Maurer
Douglas Pennell
Christoph Gaupp
Igor Nikolaevich BAYBUZENKO
Valeriya Andreevna UZBEKOVA
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Ansaldo Energia Switzerland AG
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Ansaldo Energia Switzerland AG
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Publication of EP3505725A1 publication Critical patent/EP3505725A1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means

Definitions

  • the present invention relates to a can combustor for a gas turbine for power plants.
  • the present invention relates to the interface, i.e. a sealed interface, between the cold shell and the hot shell forming a cooled liner of a can combustor for a gas turbine for power plants.
  • the present invention refers to a gas turbine for power plants comprising the above mentioned can combustor.
  • a gas turbine assembly for power plants comprises a rotor having an axis and provided with an upstream compressor sector, a combustor sector and a downstream turbine sector.
  • the terms downstream and upstream refer to the direction of the main gas flow passing through the gas turbine.
  • the compressor comprises an inlet supplied with air and a plurality of blades compressing the passing air.
  • the compressed air leaving the compressor flows into a plenum, i.e. a closed volume delimited by an outer casing, and from there into the combustor.
  • the compressed air is mixed with at least one fuel.
  • the mixture of fuel and compressed air flows into a combustion chamber where this mixture is combusted.
  • the resulting hot gas leaves the combustor and is expanded in the turbine performing work on the rotor.
  • a sequential gas turbine comprises two combustors in series wherein each combustor is provided with the relative burner and combustion chamber. Following the main gas flow direction, the upstream combustor is called “premix” combustor and is fed by the compressed air. The downstream combustor is called “sequential” or “reheat” combustor and is fed by the hot gas leaving the first combustion chamber.
  • the two combustors are physically separated by a stage of turbine blades, called high pressure turbine.
  • the sequential liner and the picture frame are realized as a single piece called transition duct configured for guiding the hot gas leaving the combustor toward the turbine, in particular toward the first vane of the turbine.
  • the reheat burner can be realized in form of a plurality of single or dual fuel injector fingers extending across the flow channel.
  • these injector fingers can be realized in form of a streamline body having preferably a lobed trailing edge. Due to the high hot gas temperature, the reheat burner is not provided with any sparker and the combustion starts as a self combustion.
  • the liner of a can combustor is defined by an inner tubular body, called hot shell and limiting the combustion chamber, and an outer tubular body called cold shell.
  • This cold shell outwardly covers at least part of the hot shell, is spaced from the hot shell for realizing a cooling air channel and defines the outer liner diameter.
  • the cold and hot shell are fixed to each other at the downstream ends, i.e. such downstream ends are fixed to a common structure that typically is the picture frame, whereas the upstream portion of the cold shell overlaps with a sliding feature an intermediate portion of the hot shell.
  • the can combustor comprises a combustor outer casing configured to be coupled with a relative portal hole provided in the gas turbine outer casing.
  • a gap is present that allows the compressed air to reach the burner, in particular the premix burner, coupled to the upstream end of the hot shell.
  • a gap is therefore inwardly limited downstream by the cold shell and upstream by the hot shell.
  • US2009282833 discloses a combustor liner comprising an inner tubular body connected to an outer tubular body in order to form a surface slip joint.
  • a primary object of the present invention is to provide a can combustor for a gas turbine wherein the can combustor comprises:
  • each combustor comprises a first burner, a first combustion chamber, a second burner, a second combustion chamber and a transition duct facing the turbine sector.
  • the hot shell extends from the downstream end of the transition duct, called picture frame, to the first burner.
  • the cold shell extends from the picture frame, or very near to the picture frame and ends connected to the hot shell in an intermediate position between the first and the second burner along an air gap between the liner and the outer combustor casing.
  • the coupling between the upstream end of the cold shell and the hot shell is a sealed coupling.
  • this coupling is performed by welding the two shells or by an interposition of a seal element (a hula seal or a piston ring) between the inner surface of the cold shell and the outer surface of the hot shell.
  • a seal element a hula seal or a piston ring
  • the first prior art does not allow relative movements of the shells but does not affect the dimension of the gap.
  • the second prior art allows relative movements of the shells but reduces the gap and increases the pressure drop.
  • the coupling between the upstream end of the outer tubular body and the inner tubular body is a direct surface contact coupling.
  • the inner surface of the upstream end of the outer tubular body rests on the outer surface of the inner tubular body without any constrain for a relative sliding of the outer tubular body with respect to the inner tubular body at least along a axial direction parallel to the combustor axis.
  • the direct surface contact coupling according to the invention is configured to realize a sealed coupling.
  • the direct surface contact coupling comprises at least a cooling air channel configured for connecting the combustion chamber with a plenum volume, i.e. the gap between the liner and the outer combustor casing, arranged outwardly the liner.
  • the cooling air channel is configured to remain open independently on the axial relative sliding of the outer tubular body with respect to the inner tubular body.
  • the cooling air channel comprises a plurality of passing slots having at least an axial extent obtained in the upstream end of the outer tubular body and at least a channel obtained in a portion the inner tubular body radially corresponding with the slot. This cooling feature allows to realize a sealed coupling with a known leakage ratio independent of the relative sliding of the outer tubular body with respect to the inner tubular body and that does not vary from combustor to combustor and over the entire operational time.
  • the direct surface contact coupling is also free to have a relative sliding of the outer tubular body with respect to the inner tubular body also along a circumferential direction centered at the combustor axis. Consequently, the cooling air channel is configured to remain open also independently of the circumferential relative sliding of the outer tubular body with respect to the inner tubular body.
  • each channel obtained in the inner tubular body comprises a circumferential groove obtained in the outer surface of the inner tubular body and a plurality of effusion holes connecting the circumferential groove with the combustion chamber.
  • the effusion holes are inclined with respect to the radial direction centered at the combustor axis to realize a film cooling along the inner surface of the inner tubular body.
  • the present invention can be preferably used in a sequential can combustor wherein the fuel is supplied to the second burner via a central lance extending inside the first combustion chamber along the combustor axis. Indeed, in this case the combustion chamber diameter cannot be limited due to the presence of the lance that already deprives the combustion chamber of available volume.
  • the present invention can be applied also in other kinds of sequential can combustors, for instance a sequential can combustor wherein the fuel supply of the sequential burner is arranged outside the combustion chamber.
  • the present invention refers also to a gas turbine for power plants comprising such a can combustor wherein preferably this can combustor is a sequential can combustor.
  • FIG. 1 is a schematic view of a gas turbine for power plants that can be provided with a burner according to the present invention.
  • a gas turbine 1 having an axis 9 and comprising a compressor 2, a combustor sector 4 and a turbine 3.
  • the compressor comprises an inlet fed by ambient air that, once compressed, leaves the compressor 2 and enters in a plenum 16, i.e. a volume defined by an outer casing 17. From the plenum 16, the compressed air enters in the combustor sector that comprises a plurality of can combustors 4 annularly arranged around the axis 9.
  • the terms downstream and upstream refer to the gas main flow direction.
  • Each can combustor 4 comprises at least a burner 5 where the compressed air is mixed with at least a fuel. This mixture is then combusted in a combustion chamber 6 and the resulting hot gas flows in a transition duct 7 downstream connected to the turbine 3.
  • the turbine 3 comprises a plurality of vanes 12, i.e. stator blades, supported by a vane carrier 14, and a plurality of blades 13, i.e. rotor blades, supported by a rotor.
  • the hot gas expands performing work on the rotor and leaves the turbine 3 in form of exhaust gas 11.
  • figure 2 is schematic view of a can combustor that can be applied in the gas turbine of figure 1 and that could be provided with the present invention.
  • a can combustor 4 comprising a combustor outer casing 35 connected to a relative portal hole 25 of an outer casing 17 defining the plenum 16 where the compressed air is delivered by the compressor 2.
  • the can combustor 4 has an axis 24 and comprises in series along the gas flow M a first combustor, or premix combustor 18, and a second combustor, or reheat combustor 19.
  • the first combustor 18 comprises a first or premix burner 20 and a first combustion chamber 21.
  • the reheat combustor 19 comprises a reheat burner 22 and a second combustion chamber 23.
  • the reheat burner can comprise a plurality of fuel injectors 26, in particular dual fuel and carrying air injectors, arranged across the burner for injecting the fuel in the passing hot gas.
  • the fuel is fed to the fuel injectors 26 by a fuel lance 27 axially extending through the first combustion chamber 21 up to the reheat burner 22.
  • the can combustor 4 Downstream the second combustion chamber 23 the can combustor 4 comprises a transition duct 28 for guiding the hot gas flow to the turbine 3.
  • the fuel lance 27 may be arranged outside the combustion chamber 21.
  • the combustion chambers 21, 23 are delimited by a liner 29 comprising an inner tubular body 30, or hot shell, having an inner surface directly in contact and heated by the hot gas flow, and an outer tubular body 31, or cold shell, covering at least in part the hot shell. Between the hot 30 and cold shell 31 a cooling air gap 32 is present. According to the disclosed embodiment of figure 2 , the cooling air is part of the compressed air that from the plenum passes through cooling holes 33 obtained in the downstream portion of the cold shell 31.
  • the terms "downstream" with reference to the liner refer to the portions near to the turbine whereas the term “upstream” refers to the portion near to the premix burner 20.
  • the upstream end 34 of the cold shell 31 is coupled to an intermediate portion of the hot shell 30 facing the outer combustor casing 35.
  • the kind of the coupling between the upstream end 34 of the cold shell 31 and the hot shell 30 will be described in detail in the following.
  • a gap 36 is present between the outer combustor casing 35 and the liner for allowing the compressed air to reach the premix burner 20 from the plenum 16.
  • Such a gap 36 is downstream defined by the cold shell 31 and the outer combustor casing 35 and upstream by the hot shell 30 and the outer combustor casing 35.
  • figure 3 is an enlarged view of the portion labelled with the reference III in figure 2 .
  • figure 3 discloses in an enlarged view the gap 36 and the upstream end 34 of the cold shell 31 connected to an intermediate portion of the hot shell 30.
  • the arrow M defines the hot gas direction inside the combustor.
  • figure 4 is an enlarged view of the portion labelled with the reference IV in figure 3 .
  • figure 4 discloses the coupling between the upstream end 34 of the cold shell 31 and the hot shell 30.
  • This coupling consists in a sliding contact coupling wherein the inner surface of the upstream end 34 of the cold shell 31 is outwardly resting on the outer surface of the hot shell 30 without any sliding constrain at least along the axial direction parallel to the combustor axis 24.
  • the axial sliding has been represented in figure 4 by the reference R.
  • the arrow C' represents the cooling air flow.
  • the contact between the inner surface of the upstream end 34 of the cold shell 31 and the outer surface of the hot shell 30 is a direct contact without the interposition of any other element, for instance a seal element like a hula seal or a piston ring.
  • this overlapping sliding contact coupling comprises also a particular cooling feature suitable for ensuring a cooling effect independently of the relative sliding movements between the hot 30 and the cold shell 31.
  • figure 5 is an enlarged view of the portion labelled with the reference V in figure 4 .
  • the arrow R refers to the radial direction with respect to the combustor axis 24.
  • Figure 5 discloses two grooves 10 realized in the outer surface of the hot shell 30 in contact with the upstream end 34 of the could shell 31.
  • figure 5 discloses the presence of effusion holes 15 connecting the grooves 10 with the combustion chamber limited by the hot shell 30.
  • the effusion holes 15 are inclined with respect to the radial direction R, in particular with an inclination directed towards the main hot gas direction M.
  • FIGS. 6 and 7 are other views of the portion disclosed in figure 5 .
  • the grooves 10 are circumferential grooves 10 extending along the circumferential direction (represented in figure 6 with the arrow C) centered on the combustor axis 24.
  • the upstream end 34 of the cold shell 31 comprises a plurality of passing slots 37 extending along the axial direction M from the edge of the upstream end 34 beyond the grooves 10.
  • the air can freely reach the grooves 10 passing through the slots 37 and from the grooves 10 can reach the combustion chamber passing through the effusion holes 15.
  • the effusion holes 15 are also inclined with respect to the axial direction M. Therefore, the cooling of the portion of the hot shell 30 is ensured by the impingement of cooling air in the grooves 10 passing by the slots 37, by convective cooling inside the grooves 10 and by a film cooling at the inner surface facing the combustion chamber.
  • the cooling feature is independent of the relative sliding in the axial direction between the hot 30 and cold shell 31 because in case of an axial sliding the slots 37 disclose an axial extension so that the grooves 10 are in any case accessible from the gap 36.
  • the grooves 10 are milled grooves and the effusion holes 15 are laser drilled effusion holes.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)

Claims (13)

  1. Rohrbrenner für eine Gasturbine (1), wobei der Rohrbrenner (4) umfasst:
    - wenigstens einen Brenner (5, 20, 22);
    - wenigstens eine Auskleidung (29), die eine Brennkammer (6, 21, 23) mit einer Brennerachse (24) definiert;
    wobei die Auskleidung (29) umfasst:
    - einen inneren rohrförmigen Körper (30);
    - einen äußeren rohrförmigen Körper (31), der wenigstens teilweise den inneren rohrförmigen Körper (30) überlappt und von dem inneren rohrförmigen Körper (30) beabstandet ist, um einen Kühlluftspalt (32) zu definieren;
    wobei der äußere rohrförmige Körper (31) ein stromaufwärtiges Ende (34) aufweist, das mit einem mittleren Abschnitt des inneren rohrförmigen Körpers (30) gekoppelt ist;
    wobei die Kopplung zwischen dem stromaufwärtigen Ende (34) des äußeren rohrförmigen Körpers (31) und dem inneren rohrförmigen Körper (30) eine direkte Oberflächenkontaktkopplung (38) der Innenfläche des stromaufwärtigen Endes (34) des äußeren rohrförmigen Körpers (31) ist, die auf der Außenfläche des inneren rohrförmigen Körpers (30) liegt, wobei die direkte Oberflächenkontaktkopplung (38) dafür konfiguriert ist, ein relatives Gleiten des äußeren rohrförmigen Körpers (31) bezüglich des inneren rohrförmigen Körpers (30) wenigstens entlang einer axialen Richtung (M) parallel zur Brennerachse (24) zu ermöglichen;
    dadurch gekennzeichnet, dass die direkte Oberflächenkontaktkopplung (38) wenigstens einen Kühlluftkanal umfasst, der dafür konfiguriert ist, die Brennkammer (6, 21, 23) mit einem Luftkammervolumen (36) zu verbinden, das außerhalb der Auskleidung (29) angeordnet ist, wobei der Kühlluftkanal mehrere axiale Durchgangsschlitze (37), die in dem stromaufwärtigen Ende (34) des äußeren rohrförmigen Körpers (31) erhalten werden, und wenigstens einen Kanal (10, 15) umfasst, der in einem Abschnitt des inneren rohrförmigen Körpers (30) erhalten wird, der mit dem Schlitz (37) korrespondiert.
  2. Rohrbrenner nach Anspruch 1, wobei die axialen Durchgangsschlitze (37) von der Endkante des stromaufwärtigen Endes (34) des äußeren rohrförmigen Körpers (31) ausgehen.
  3. Rohrbrenner nach Anspruch 1 oder 2, wobei die direkte Oberflächenkontaktkopplung (38) ein relatives Gleiten des äußeren rohrförmigen Körpers (31) bezüglich des inneren rohrförmigen Körpers (30) auch entlang einer Umfangsrichtung (C) zentriert an der Brennerachse (24) ermöglicht.
  4. Rohrbrenner nach Anspruch 3, wobei jeder in dem inneren rohrförmigen Körper (30) erhaltene Kanal (10, 15) eine in der Außenoberfläche des inneren rohrförmigen Körpers (30) erhaltene Umfangsnut (10) und mehrere Effusionslöcher (15), die die Umfangsnut (10) mit der Brennkammer (6, 21, 23) verbinden, aufweist.
  5. Rohrbrenner nach Anspruch 4, wobei sich die Umfangsnut (10) entlang des gesamten inneren rohrförmigen Körpers (30) erstreckt.
  6. Rohrbrenner nach Anspruch 4 oder 5, wobei die Umfangsnut (10) durch Fräsen ausgebildet ist.
  7. Rohrbrenner nach einem der vorangehenden Ansprüche 4 bis 6, wobei die Effusionslöcher (15) bezüglich der radialen Richtung (R) zentriert an der Brennerachse (24) geneigt sind.
  8. Rohrbrenner nach Anspruch 7, wobei die Effusionslöcher (15) eine Neigung aufweisen, die in Richtung zu der Haupt-Heißgasrichtung (M) ausgerichtet ist.
  9. Rohrbrenner nach einem der vorangehenden Ansprüche 4 bis 8, wobei die Effusionslöcher (15) durch Laserbohren ausgebildet sind.
  10. Rohrbrenner nach einem der vorangehenden Ansprüche, wobei der Rohrbrenner der Reihe nach einen ersten Brenner (20), eine erste Brennkammer (21), einen zweiten Brenner (22), eine zweite Brennkammer (23) und einen Übergangskanal (28) umfasst; wobei sich der äußere rohrförmige Körper (31) von dem stromabwärtigen Ende des Übergangskanals (28) bis zu einer Zwischenposition zwischen dem ersten (20) und dem zweiten Brenner (22) erstreckt.
  11. Rohrbrenner nach Anspruch 10, wobei der Rohrbrenner ein äußeres Brennergehäuse (35) umfasst, das dafür konfiguriert ist, mit einem Portalloch (25) der Gasturbine gekoppelt zu werden; wobei die Auskleidung (29) und das äußere Brennergehäuse (35) beabstandet sind, um einen Spalt (36) auszubilden.
  12. Rohrbrenner nach Anspruch 10 oder 11, wobei der Rohrbrenner eine Brennstofflanze (27) umfasst, die sich innerhalb der ersten Brennkammer (21) entlang der Brennerachse (24) erstreckt, um dem zweiten Brenner (22) Brennstoff zuzuführen.
  13. Gasturbine für ein Kraftwerk; wobei die Gasturbine (1) eine Achse (9) aufweist und der Gasströmungsrichtung folgend umfasst:
    - einen Verdichterabschnitt (2) zum Verdichten von Umgebungsluft,
    - einen Brennerabschnitt (4) zum Mischen und Verbrennen der verdichteten Umgebungsluft mit wenigstens einem Brennstoff,
    - wenigstens einen Turbinenabschnitt (3) zum Entspannen des verbrannten Heißgasstroms, der aus dem Brennerabschnitt (4) austritt und Arbeit an einem Rotor (8) leistet;
    wobei der Brennerabschnitt (4) wenigstens einen Rohrbrenner nach einem der vorangehenden Ansprüche umfasst.
EP18215866.7A 2017-12-26 2018-12-24 Rohrbrenner für eine gasturbine und gasturbine mit solch einem rohrbrenner Active EP3505725B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2017145745A RU2761262C2 (ru) 2017-12-26 2017-12-26 Трубчатая камера сгорания для газовой турбины и газовая турбина, содержащая такую трубчатую камеру сгорания

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EP3505725B1 true EP3505725B1 (de) 2020-10-21

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RU2017145745A3 (de) 2021-07-05
RU2017145745A (ru) 2019-06-26
EP3505725A1 (de) 2019-07-03
RU2761262C2 (ru) 2021-12-06
CN110030583A (zh) 2019-07-19
CN110030583B (zh) 2022-07-08

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